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AERODINÀMICA (Curs Total)

AERODINÀMICA (Curs Total)

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The

image shows a vortex line with horseshoe shape. The vortex line has different

intensity per unit length depending on the considered segment/leg of the

horseshoe, where

92 m/s. The vortex line follows the

axis from point A to the origin O; then, it follows the

axis from O

to point B (

), where 5,1

m, and finally it goes from point B to point E.

Compute the

-axis component of the flow velocity [m/s] in a point located

in the position

-3,6 m and 5,1

, as induced by the vortex line segments AO, OB, and BE, when A and E are

located in the infinite

. Recall that

the positive direction of the

axis is perpendicular to the screen,

pointing out of the screen (that is, toward ourselves)

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Consider

a rectangular wing with

chord m and wing span m,

flying

horizontally in steady atmosphere with velocity

m/s (). The air density is 1 kg/m³ and the circulation distribution along the wing span is:

Compute the wing lift in Newtons (provide at least 2 decimals, and use the coma "," as decimal separator).

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Say that we have a 3D wing which is entirely built using only a single type of airfoil. The aspect ratio of the wing is AR=16,6. As per the relationship between the vs polar curve of the 3D wing and the vs polar curves of the 2D airfoils it is made of, what is the value of in [º] at which 0,51 for the 3D wing, if the value of at which 0,51 for the 2D airfoils is 2,1º?

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Consider

a rectangular wing with

chord m and wing span m,

flying

horizontally in steady atmosphere with velocity

m/s (). The air density is 1 kg/m³ and the circulation distribution along the wing span is:

exercise 2.7v4q3v0_circulation

with m²/s. Compute the induced drag coefficient for this wing (provide at least 4 decimals, and use the coma "," as decimal separator).

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In Prandtl’s wing

theory:

originally, it was only

valid for low aspect ratio wings

originally, it was only

valid for rectangular wings

the induced drag in a

wing is due to the component of the airfoil lift on the direction perpendicular

to the free stream velocity

it provides more

information about the lift distribution along the chords of the airfoils

compared to the 2D linear potential theory

none

of the other options is correct

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Which statement is true about D'Alembert's paradox within the frame of

lifting-line theory?

It applies both to the

individual airfoils comprising the wing and to the wing itself

It applies to the full

wing but not to the individual airfoils comprising it

applies locally to the individual airfoils comprising the wing but not to the

wing itself

It applies neither to

the full wing nor to the individual airfoils comprising it

D'Alembert's paradox is

utterly irrelevant to lifting-line theory

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For a laminar boundary

layer (BL) at an angle of attack (AOA) well below the stall AOA:

the friction drag is

larger compared to the case of turbulent BL

if any, the flow

detachment point is usually closer to the TE compared to the case of turbulent

the BL

is always laminar at the beginning

if existing, the wake or

pressure drag is smaller compared to the case of turbulent BL

none of the other options is correct

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Say we have a doublet with intensity 5 [m³/s], a source with intensity -27 [m²/s], and a vortex with intensity 39 [m²/s], all three located in the origin of the wind reference frame. You are asked to compute the axis component of the flow velocity in units [m/s], in the position 4,4 m and 18,3 m.